RU2253825C1 - Method for functioning of missile information-computer system and device for its realization - Google Patents

Abstract

FIELD: aircraft guided missiles.

SUBSTANCE: on the basis of the source information on the target attitude and range to it, the rate of missile closure, geometrical dimensions of the target, miss of the missile are determined in the immediate proximity from it, and a command is formed for blasting the missile warhead on the basis of this information with due account made for the initial speed of scattering of the missile warhead fragments. The method is realized by a device, having a key and a computer forming the command for blasting the missile warhead, whose first and second inputs are connected respectively to the first and second outputs of the information processing module, the third input is connected to the output of the reflected signal receiver, the first output is connected to the second input of the key, whose first input is connected to the second output of the antenna control channel, and the key output is connected to the first input of the power amplifier and antenna drive, whose second input is connected to second output of the amplifier forming the command for blasting the missile warhead, whose third output serves as the output of the command for blasting the missile warhead.

EFFECT: enhanced functional potentialities of guidance due to informational support of functioning of the fighting equipment.

11 cl, 8 dwg

Description

The invention relates to the field of aviation guided missiles and can be used to solve the problem of guiding a missile at an air target and for providing information support for the functioning of AUR combat equipment.

There is a known method of functioning of a rocket information-computing system, which consists in measuring the parameters of the target’s motion and the rocket’s own motion, forming the necessary parameters of relative and absolute motion that are not directly measurable, using a priori information, choosing the method of guiding the rocket at the target that is best for any or a criterion for these conditions of use, an analysis of the interference environment and the inclusion, depending on the situation, of the means of noise protection, non-radio technology Sgiach meters, retargeting missiles in jammer, the formation and preparation of the control signal for the fuze (Merkulov, V.N.Lepin aeronautical radio system -. M .: Radio and communication, 1997, at s.201).

A device is known, which includes a serially connected synchronization signal receiver, a reflected signal receiver, as well as a system of autonomous sensors and an information processing module, a computer and a power amplifier, the output of the synchronization receiver being connected to the first input of the information processing module, the output of the reflected signal receiver with a second the input of the information processing module, the first and second output of the sensor system, respectively, with the third and fourth inputs of the information processing module, the fifth input to It is connected to a power amplifier and an antenna drive, which is mechanically connected to the antenna, the first, second, third, and fourth outputs of which are connected respectively to the control and feedback signal bus to the fighter’s equipment, to the first and second input of the mismatch parameters calculator, to the amplifier input power and drive the antenna, the output of which has a mechanical connection with the antenna (Merkulov V.I., Lepin V.N.Aircraft radio control systems. - M.: Radio and Communications, 1997, p. 201).

The disadvantage of this method and device is the poor information support for the functioning of the AUR combat equipment due to the lack of the possibility of obtaining additional information about the air target and its motion parameters on board the rocket.

An object of the invention is to increase the effectiveness of the combat use of missile defense by using additional information about the air target and the parameters of its movement in the interests of the combat equipment of the anti-aircraft missile class "in-in."

The solution to the technical problem is achieved by the fact that in the method of functioning of the information and computing system of the rocket, which consists in measuring the parameters of the target’s motion and the rocket’s own motion, forming the necessary parameters of relative and absolute motion, not amenable to direct measurement, based on the use of a priori information, choosing the method of guiding the rocket for the purpose that is best by any criterion for the given conditions of use, analysis of the interference environment and inclusion, depending on the situation novelties of anti-jamming equipment and non-radio technical meters, redirecting a rocket to an jammer, generating a training and control signal for a radio fuse, additionally determine, based on the initial information about the angular position and range to the target, in the immediate vicinity of the target, the speed of approach of the rocket, the geometric dimensions of the target, miss missiles and form a team to undermine the warhead of the rocket based on this information, taking into account the initial speed of the flight of fragments of the warhead of the rocket.

The speed of approach of the rocket in the immediate vicinity of the target is determined at the moment the target passes the second and third fixed distances in the form of the expression:

where Z ₂ , Z ₃ are the second and third fixed distances to the target, τ is the time interval proportional to the target’s speed when passing through these fixed distances. The linear size of an extended target is determined at the moment it passes the second fixed distance, by scanning it with a radiation diagram and fixing the angular positions and the distance to the starting and ending points on an extended target, respectively, at the time of the appearance and disappearance of the reflected signal from the target in the form of the expression:

where D ₁ , d ₂ - the angular position of the start and, respectively, the end point on the target body; Δ φ = φ _n -φ _to - the angular size of the target.

The miss miss value is determined in the form of the expression:

where A, B, C are constant coefficients, r ₁ , r ₂ , r ₃ are the current distances recorded during the passage of the target three given distances.

A command to undermine the warhead of a rocket is formed in the form of an expression:

where V ₀ is the initial velocity of the expansion of fragments.

To a device for implementing a method of operating an information-computing system, comprising a serially connected antenna and a receiver of a synchronization signal, an antenna and a receiver of a reflected signal, an information processing module and a mismatch parameter calculator, as well as an autonomous sensor system, a power amplifier and an antenna drive, an information processing module, consisting of a device for searching, detecting, selecting and analyzing signals, a channel for estimating the range and speed of approach, an antenna control channel where its output is mechanically connected with the reflected antenna, the output of the reflected signal receiver is connected to the first input of the information processing module, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the synchronization signal receiver, the first and second output of the system autonomous sensors, with the output of the training and target designation commands from the fighter equipment, which are simultaneously connected to the third input of the mismatch parameters calculator, with the output of the autonomous calculator system, the first output of the power amplifier and the antenna drive, the second output of which is mechanically connected to the antenna of the reflected signal, while the first, second third, outputs of the information processing module are connected respectively to the input of the control and feedback signals of the fighter equipment, the first and second input of the parameter calculator inconsistencies, in addition, the second output of the synchronization receiver is connected to the second input of the reflected signal receiver, an additional key and a computer for generating a command for the first part of the rocket, the first, second inputs of which are connected respectively to the first and second outputs of the information processing module, the third input is the output of the reflected signal receiver, the first output is connected to the second key input, the first input of which is connected to the second output of the antenna control channel, and the output the key is connected to the first input of the power amplifier and the antenna drive, the second input of which is connected to the second input of the computer forming the command to undermine the warhead of the rocket, the third input of which is the output of the coma dy at undermining warhead missiles.

In addition, the command formation calculator for undermining the warhead of a rocket consists of a block for fixing the current parameters of the target’s movement, a block for determining missile missiles, a block for determining the geometric dimensions of the target, a block for forming a command for undermining the warhead of a rocket, the first and second inputs of the block for fixing the current motion parameters the target and the unit for determining the geometric dimensions of the target are connected respectively to the output of the channel for estimating the range and speed of approach of the target and the output of the antenna control channel, first, w The third, fourth, fifth and fifth and sixth outputs of the block for fixing the current target motion parameters are connected, respectively, with the first, second and third inputs of the missile miss detection unit, with the second, third input of the command formation unit for detonating the missile warhead and the third and fourth input of the geometric determination unit the size of the target, the fifth input of which is connected to the output of the reflected signal receiver, and the first output is the second output of the team formation calculator to undermine the warhead of the rocket and connected to the first the input of the power amplifier and the drive of the antenna, the second and third outputs of the unit for determining the geometric dimensions of the target are connected respectively to the fourth and fifth inputs of the unit for forming a team to detonate the missile warhead, the first input of which is connected to the output of the missile miss detection unit, and the output is the third output of the formation calculator teams to undermine the warhead of the rocket.

In addition, the unit for fixing the current target motion parameters consists of a functional converter, a first multiplier of the first, second and third comparison circuits, a first, second and third storage device, as well as a constant signal generator, the input of the functional converter being connected to the output of the antenna control channel, and the output with the first input of the first multiplier, the second input of which is connected to the output of the channel for assessing the range and approach speed, and the output with the first inputs of the first, second, third circuits the second inputs of which are connected respectively to the first, second and third outputs of the constant signal generator, and the fourth output is connected to the second input of the command formation unit for undermining the warhead of the rocket, the output of the comparison circuits are connected respectively by the first inputs of the first, second and third storage devices, the second inputs of which are connected to the output of the channel for estimating the range and approach speed.

In addition, the missile miss detection unit consists of the first, second and third quadrants, second, third multipliers, the first subtracting and second summing device, the second functional converter, as well as the second constant signal generator, the first, second, third outputs of the block fixing the current the motion parameters of the target are connected to the inputs of the first, second and third quadrator, the outputs of which are connected respectively to the first inputs of the second, third and fourth multipliers, the second inputs of which connected to the first, second and third outputs of the second constant signal generator, respectively, the outputs of the second and third multipliers are connected to the first and second inputs of the first subtractor, the output of which is connected to the first input of the second summing device, the second input of which is connected to the output of the fourth multiplier, and the output the second summing device is connected to the input of the second square root extraction functional converter, the output of which is connected to the first input of the command generation unit at undermining warhead missiles.

In addition, the unit for determining the geometric dimensions of the target consists of an element AND, an AND element, a pulse generator, a pulse counter and a series-connected shift register, a digital-to-analog converter, as well as a third, fourth, fifth and sixth storage device, a third and a fourth quadrator, the third adder, the second and third subtractor, the third and fourth functional converter, the fifth multiplier of the third constant signal generator, and the output of the receiver is reflected of the signal is connected to the first input of the AND element, and simultaneously the input of the AND element, the output of the block for fixing the current parameters of the target’s movement is connected to the second input of the And element, the output of which is connected simultaneously with the input of the pulse generator, the first inputs of the third and fifth storage devices, the second inputs which are connected respectively to the output of the range estimation channel and the antenna control channel, the output of the NAND element is connected to the first inputs of the shift register, the fourth and sixth storage devices, the output d channel for assessing the range and speed of approach is connected to the inputs of the third and fourth storage devices, the outputs of which are connected respectively to the inputs of the third and fourth quadrator, the outputs of which are connected to the first and second input of the third adder, the output of which is connected to the first input of the second subtractor, the output of the fifth and the sixth storage device is connected respectively to the first and second inputs of the third subtractor, the output of which is connected to the input of the functional transform a device whose output is connected to the first input of the fifth multiplier, the second and third input of which is connected respectively to the output of the third and fourth storage devices, and the output is connected to the second input of the second subtractor, the output of which is connected to the input of the fourth functional converter, the output of which is connected to the third the input of the command formation unit to undermine the warhead of the rocket, the output of the pulse generator is connected to the first input of the pulse counter, and the second input is connected to the sixth output of the fixation unit t current parameters of the target’s movement, and the counter’s output is the second output of the target's geometric dimensions block, the first and third output of which is the output of the digital-analog converter and the fourth functional converter.

In addition, the unit for forming a command to undermine the warhead of a rocket consists of a first, second and third divider, a fourth subtracting device, and the fourth output of the block for fixing the current parameters of the target’s movement, the output of the block for determining the miss and the third output of the block for determining the geometric dimensions of the target are connected to the first inputs of the first, second and third divider, the output of the channel for estimating the range and approach speed is connected simultaneously with the second inputs of the first and third divider, the fifth output of the latching unit The parameters of the target’s motion are connected to the second input of the second divider, the outputs of the first, second, and third dividers are connected, respectively, to the first, second, and third inputs of the fourth subtractor, the output of which is the output of the command formation unit to undermine the warhead of the rocket.

Comparative analysis with the prototype shows that the inventive method and device are distinguished by the presence of new actions and new circuit elements and new connections that provide the technical result of the invention, which allows us to conclude that in this technical solution the patentability criterion is "novelty", namely in the method:

1) determine the speed of approach of the rocket with the goal at the time of passage of the second and third fixed distances;

2) determine the geometric dimensions of the target;

3) determine the missile missile relative to the target;

4) form a team to detonate the warhead of the rocket based on this information, taking into account the speed of the flight of fragments of the warhead of the rocket, and the key and the calculator of the formation of the team to detonate the warhead of the rocket are entered into the device.

Comparison of the proposed solution with other technical solutions shows that it does not explicitly follow from the prior art, the claimed method and device have expanded functionality by controlling the moment of operation of the AUR warhead in accordance with the specific conditions of the missile’s approach to the target.

This allows us to conclude that the claimed invention meets the criterion of "significant differences".

Figure 1 shows the structural diagram of the information and computing system of the rocket, figure 2, 3 is a diagram of the rapprochement of the rocket with the goal, figure 4 is a structural diagram of the computer calculator formation to detonate the warhead of the rocket, figure 5 is a block fixing current parameters movement of the target, in Fig.6 is a block for determining miss; in Fig.7 is a block for determining the geometric dimensions of the target, Fig.8 is a block forming a team to undermine the warhead of the rocket.

The device (Fig. 1) for the operation of an information-computing system, comprises a series-connected antenna 1 and a synchronization signal receiver 2, an antenna 3 and a reflected signal receiver 4, an information processing module 5 and a mismatch parameter calculator 6, as well as an autonomous sensor system 7, an amplifier 8 power and antenna drive, a key 12 and a computer 13 forming a command to detonate the warhead of the rocket, the information processing module 5 consists of a device 9 for searching, detecting, selecting and analyzing signals, channel 10 range and speed of approach, channel 11 control the antenna, and its output is mechanically connected to the antenna 3 of the reflected signal, the output of the receiver 4 of the reflected signal is connected to the first input of the information processing module 5, the second, third, fourth, fifth, sixth, seventh inputs of which, respectively connected to the first output of the receiver 2 synchronization signals, the first and second output of the system 7 of autonomous sensors, with the output of the training and target designation commands from the equipment of the fighter, which are simultaneously connected to the third the math of the calculator 6 mismatch parameters, with the output of the calculator of the autonomous system, the first output of the power amplifier 8 and the antenna drive, the second output of which is mechanically connected to the antenna 3 of the reflected signal, while the first, second, third, outputs of the information processing module 5 are connected respectively to the input of the control signals and feedback of the fighter equipment, the first and second input of the calculator 6 mismatch parameters, in addition, the second output of the synchronization receiver 2 is connected to the second input of the reflection receiver 4 of the signal, the first, second inputs of the calculator 13 for forming a command to detonate the warhead of the rocket are connected respectively to the first and second outputs of the information processing unit 5, the third input to the output of the reflected signal receiver 4, the first output connected to the second input of the key 12, the first input of which is connected with the second output of the antenna control channel 11, and the output of the key 12 is connected to the first input of the power amplifier 8 and the antenna drive, the second input of which is connected to the second input of the command generation calculator 13 parts of the rocket, the third entrance of which is the output of the team to undermine the warhead of the rocket.

The calculator 13 of the formation of a command to detonate the warhead of a rocket consists of a block 14 for fixing the current parameters of the target’s movement, a block 15 for determining miss missions, a block 16 for determining the geometric dimensions of the target, block 17 for forming a team for undermining the warhead of a rocket, the first and second inputs of block 14 of fixation the current parameters of the motion of the target and the block 16 for determining the geometric dimensions of the target are connected respectively to the output of the channel 10 for estimating the range and speed of approach of the target and the output of the antenna control channel 11, the first , the second third, fourth and fifth and sixth outputs of the block 14 for fixing the current target motion parameters are connected, respectively, with the first, second and third input of the missile miss detection block 15, with the second, third input of the command formation block 17 for detonating the missile warhead and the third and fourth the input of the block 16 for determining the geometric dimensions of the target, the fifth input of which is connected to the output of the receiver 4 of the reflected signal, and the first output is the second output of the calculator 13 forming a team to undermine the warhead of the rocket and is connected to the first input of the power amplifier 8 and the antenna drive, the second and third output of the target geometric determination unit 16 are connected respectively to the fourth and fifth input of the command formation unit 17 for detonating the missile warhead, the first input of which is connected to the output of the missile miss detection unit 15, and the output is the third output of the calculator 13 team formation to undermine the warhead of the rocket.

Block 14 for fixing the current parameters of the target’s movement consists of a functional converter 18, a first 19 multiplier, a first 20, a second 21 and a third 22 comparison circuit, a first 23, a second 24 and a third 25 storage device, as well as a constant signal generator 26, the input of the functional converter 18 is connected to the output of the antenna control channel 11, and the output is connected to the first input of the first 19 multiplier, the second input of which is connected to the output of the channel 10 for estimating the range and approach speed, and the output with the first inputs of the first 20, second 21, by a loop 22 of the comparison circuit, the second inputs of which are connected respectively to the first, second and third output of the constant signal setter 26, and the fourth output of which is connected to the second input of the command formation block 17 to detonate the warhead of the rocket, the outputs of the first 20, second 21, third 22 circuits comparisons are connected, respectively, by the first inputs of the first 23, second 24, and third 25 storage devices, the second inputs of which are connected to the output of the channel 10 for estimating the range and approach speed.

Block 15 missile missile determination consists of the first 27, second 28 and third 29 quadrator, second 30, third 31 and 32 multipliers, the first 33 subtracting and second 34 totalizing device, the second 35 functional Converter, as well as the second 36 constant signal generator, and the first, second, third outputs of the block 14 for fixing the current parameters of the motion of the target are connected to the input of the first 27, second 28 and third 29 of the quadrator, the outputs of which are connected respectively to the first inputs of the second 30, third 31 and fourth 32 multipliers, the other inputs of which are connected to the first, second and third outputs of the second 36 constant signal generator, respectively, the outputs of the second 30 and third 31 multipliers are connected to the first and second inputs of the first 33 subtractor, the output of which is connected to the first input of the second 34 summing device, the second input of which connected to the output of the fourth 32 multiplier, and the output of the second 34 summing device is connected to the input of the second 35 square root extraction functional converter, the output of which is connected to the first the course of the block 17 formation of the team to undermine the warhead of the rocket.

Block 16 for determining the geometric dimensions of the target consists of an element And 37, an AND-NOT element 38, a pulse generator 39, a pulse counter 40 and a series-connected shift register 41, a digital-to-analog converter 42, and also from the third 43, fourth 44, fifth 45 and sixth 46 a storage device, a third 47 and a fourth 48 quadrator, a third 49 adder, a second 50 and a third 51 subtractor, a third 52 and a fourth 53 functional converter, a fifth 54 multiplier, a third 55 constant signal generator, and the output of the receiver 4 of the reflected signal is connected to the first input of the AND 37 element, and simultaneously the input of the AND-NOT 38 element, the output of the block 14 for fixing the current parameters of the target movement is connected to the second input of the AND 37 element, the output of which is connected simultaneously with the input of the pulse generator 39, the first inputs the third 43 and fifth 44 of the storage device, the second inputs of which are connected respectively to the output of the range estimation channel 10 and the antenna control channel 11, the output of the AND-NOT element 38 is connected to the first inputs of the shift register 41, fourth 45th and sixth 46th storage device, the output of the channel 10 for estimating the range and approach speed is connected to the inputs of the third 43 and fourth 44 storage devices, the outputs of which are connected respectively to the inputs of the third 47 and fourth 48 quadrants, the outputs of which are connected to the first and second input of the third 49 the adder, the output of which is connected to the first input of the second 50 subtractor, the output of the fifth 45 and sixth 46 of the storage device is connected respectively to the first and second inputs of the third 51 subtractor the output of which is connected to the input of the functional converter 52, the output of which is connected to the first input of the fifth multiplier 54, the second and third input of which is connected respectively to the output of the third 43 and fourth 44 memory devices, and the output is from the second input of the second 50 subtractor, the output of which is connected with the input of the fourth 53 functional converter, the output of which is connected to the third input of the command formation block 17 to detonate the missile warhead, the output of the pulse generator 39 is connected to the first input tchika 40 pulses and a second input coupled to a sixth output current parameters fixing unit 14 the target moves, and the output of counter 40 is a second output 16 of the geometric dimensions purpose, the first and third output which is respectively output digital to analog converter 42 and the fourth function converter 53.

Block 17 forming a team to undermine the warhead of a rocket consists of a first 56, second 57 and third 58 divider, third 59 subtracting device, the fourth output of block 14 fixing the current parameters of the target’s movement, the output of block 15 for determining miss and the third output of block 16 for determining geometric dimensions targets are connected to the first inputs of the first 56, second 57 and third 58 dividers, the output of the channel 10 for evaluating the range and approach speed is connected simultaneously with the second inputs of the first 56 and third 58 dividers, the fifth output of the block 14 f the coding of the current parameters of the target’s movement is connected to the second input of the second 57 dividers, the outputs of the first 56, second 57 and third 58 dividers are connected respectively to the first, second and third inputs of the fourth 59 subtractor, the output of which is the output of the command formation block 17 for undermining the warhead of the rocket .

The device operates as follows.

The functioning of the IV-V-V missile's IVS is carried out in the following modes: target designation, search and target detection while capturing it on the trajectory, formation of a mismatch parameter and formation of a command to undermine the warhead of the rocket.

The first two modes are preparatory, and the actual homing and formation of a team to undermine the warhead of the rocket is carried out in the third mode. In the target designation mode (CC) from the equipment of the fighter to the information processing module 5, instructions are received for preparing the rocket for operation and command for the control (Fig. 1). According to the preparation commands, supply voltages to the IVS are supplied, the receivers of 2, 4 synchronization channels and the reflected signal are tuned to the frequency of the target illumination signal (TWS), and the operability of the entire rocket equipment is tested. According to the commands of the control center, the meters and calculators are prepared for tracking the target selected for destruction. In accordance with these commands, the antenna 3 of the homing head is deployed in the direction of the target, or at the anticipated point at which the target will be located at the time of taking it for auto tracking. The presence of target designation commands for the range D _tsu and the approach speed V _tsu is determined by the guidance method used and the target illumination signal.

If a continuous TWS is used in the CWG, then the command of the control center is given for the approach speed V _cu (Doppler frequency), according to which radio signals will be selected only for that target, the approach speed with which corresponds to the target designation speed. If the CSG SPO uses pulse, the processing unit 5 receives the command MC by range, whereby the reflected signal receiver will be unlocked only during the arrival of the signals reflected from the target, separated from the fighter in the desired distance D _zu. With a quasi-continuous TWS, the command of the control center is given both in range and speed. In addition, the command of the control center in range, approach speed, and angular velocities of the line of sight comes as initial conditions to computers that extrapolate the relative motion of the rocket and the target in the autonomous mode of the IVS, preceding the capture of the target on the trajectory, and in the event of interference with it. The readiness of the IVS for operation is monitored by special control signals supplied to the fighter’s equipment via feedback circuits (Fig. 1).

It should be noted that, depending on the type of target illumination signal (TWS), the search and selection of the signal reflected from the intercepted target are performed differently.

After the coincidence in time of the tracking half-gates of the rangefinder and the pulse u _c reflected from the target, the search stops and the detection problem is solved. In the process of solving this problem, signals are accumulated, with the aim of increasing the probability of correct detection. In addition, the detected signal is analyzed for its belonging to the target or to the jammer. The analysis is performed according to the energy criterion, since the direct signal of active interference is many times higher than the signal reflected from the target.

If in the process of analysis it is decided that the detected signal belongs to the jammer, then the noise immunity means is turned on, the measurement results and extrapolation of autonomous sensors continue to be used, or the rocket is redirected to the jammer. In the latter case, a direct guidance method is used.

If a decision is made about the ownership of the detected signal of an intercepted target, then the IVS meters go into automatic tracking of the target in range and direction, and the IVS is transferred to the mode of generating a mismatch (homing) parameter and forming a command to undermine the warhead of the rocket.

и

а в угломерном канале 11 оценки углов

и приращений угловых скоростей

. Оценки

и

, 2, а также рассчитываемые вычислителем автономной системы (АС) оценки

используются для формирования параметра рассогласования

а оценки

- для вычисления параметров рассогласования

при методе наведения с постоянным углом упреждения.In this mode, estimates are generated in the rangefinder channel 10

and

and in the goniometer channel 11 angle estimates

and increments of angular velocities

. Grades

and

, 2, as well as estimates calculated by the calculator of the autonomous system (AC)

used to form the mismatch parameter

and grades

- to calculate the mismatch parameters

with the guidance method with a constant lead angle.

If the rocket is guided by the algorithm in the form of an expression:

в горизонтальной плоскости и

in the horizontal plane and

в вертикальной, то в угломерном канале еще формируются оценки

поперечных ускорений цели. Знание оценки Д позволяет селектировать по дальности импульсы, отраженные от перехватываемой цели, путем отпирания приемника 4 отраженных сигналов только на время их прихода. Эта особенность позволяет повысить помехозащищенность ИВС в целом.

in the vertical, then in the goniometer channel estimates are still formed

lateral acceleration of the target. Knowing the estimate of D allows you to select the range of pulses reflected from the intercepted target by unlocking the receiver 4 of the reflected signals only for the time of their arrival. This feature allows to increase the noise immunity of the IVS as a whole.

The reference point for estimating the range is set by the TWS pulses supplied to the receiver 2 of synchronization signals through the antenna 1.

.In space (direction), the target is selected due to the directional properties of the antenna 3 by turning it in the direction determined by the estimates of the angles

.

где

- оценка скорости, экстраполированной в автономной системе наведения ракеты. Поиск осуществляется путем изменения по линейному закону частоты специального гетеродина. При некотором значении этой частоты сигнал промежуточной частоты приемника отраженных сигналов (ПРМОС) попадает в узкополосный фильтр, после чего поиск прекращается и начинается этап обнаружения и анализа.With a continuous TWS, for the selection of signals reflected from the target, the Doppler frequency F _{rts is used} , which is proportional to the speed of approach of the rocket to the target. In a semi-active CWG, the frequency F _rc is allocated as the frequency difference of the two signals. One of them, reflected from the target, received by the antenna 3 A _os and amplified in the receiver 4 of the reflected signals, contains a Doppler frequency offset due to the speed of approach of the fighter with the target and target with the rocket. The second signal u _{c '} received by the antenna 1 and amplified by the receiver 2, contains the Doppler frequency shift caused by the speed of removal of the rocket from the fighter. After subtracting the frequencies of the signals entering the receivers 4, 2 of the reflected and synchronizing signals, a signal is generated, the search and selection of which is performed in the processing module 5. At a range of D _p ≤ D _{c, the} search for this signal is carried out relative to the frequency F _tsu = 2V _tsu / λ, which is set by the target designation team V _tsu at the speed measured in the radar of the fighter. If D _p > D _{s the} search is performed relative to the frequency

Where

- an estimate of the speed extrapolated to an autonomous missile guidance system. The search is carried out by changing according to the linear law of the frequency of a special local oscillator. At a certain value of this frequency, the signal of the intermediate frequency of the reflected signal receiver (PRMOS) enters the narrow-band filter, after which the search stops and the detection and analysis stage begins.

The selectable signal is analyzed for its belonging not only to the target, or to the jammer, but also to the ground. This eliminates the capture and tracking of a signal reflected from the ground, instead of a signal reflected from a low-flying target. The analysis is based on the energy and frequency differences of the signals emitted by the director of the interference and reflected from the ground or from the target.

Making a decision on whether the detected signal belongs to the jammer leads to the same thing as when using pulsed signals, namely if it is decided that the detected signal belongs to the ground, a command is issued to resume the search for the target signal in frequency. When deciding whether the analyzed signal belongs to the intercepted target, the CWG meters switch to its automatic tracking according to the Doppler frequency performed by the auto-selector (channel 10 of estimation V _sat ) and in the direction carried out by the goniometer, and the CWG switches to homing mode.

The estimate formed by the auto-selector speed based on the measurement of the Doppler frequency F _rc , enters the calculator 6 mismatch parameters for the implementation of guidance methods. The goniometer channel 11 with a continuous TWS functions in the same way as with a pulsed signal with LF.

и скорости

. При этом Д оценивается по времени запаздывания отраженного сигнала, а скорость по частоте F_рц. Наличие информации о дальности позволяет повысить помехозащищенность РЭСУ за счет отпирания приемника только на время прихода сигналов, отраженных от цели.When using a quasicontinuous signal, the search and selection of the target is performed both in range and in Doppler frequency. In the process of detecting a target, the same signal analysis takes place on its belonging to the jammer, ground or target, as when using a continuous TWS. After switching to automatic tracking of the target in range, speed and direction of the evaluation device, D and V _cb form range estimates

and speed

. In this case, D is estimated by the delay time of the reflected signal, and the speed by frequency F _rts . The availability of information on the range allows to increase the noise immunity of the RESU due to the unlocking of the receiver only at the time of arrival of signals reflected from the target.

With a quasi-continuous TWS, it is necessary to eliminate the ambiguity of the range reading, since the delay time of the reflected signal can exceed the pulse repetition period of the TWS. If it is impossible to ensure the uniqueness of the reference, the range is not estimated and tracking is not implemented. In this situation, the reflected signal is selected not by range, but by the repetition period, which also allows the receiver to be gated for the time of arrival of the reflected pulses. The expediency of this technique is due to the fact that when calculating the mismatch parameters, knowledge of the current range is not required. The principle of operation of the goniometer channel 11 remains the same as when using TWS of other types.

и рысканья ψ . На основе измерения j_x и j_1,2 в вычислители автономной системы формируются оценки

и

, используемые при вычисления параметров рассогласования. Гироскопические датчики позволяют развязать антенну 3 РГС от угловых колебаний ракеты, что повышает точность и устойчивость сопровождения целей по направлению. Обработка исходной информации о дальности и угловом положении цели в вычислителе 13 позволяет получить дополнительную информацию о скорости и промахе ракеты относительно геометрического центра цели, а также о ее геометрических размерах. Рассмотрим схему сближения ракеты с целью (фиг.2).The self-motion parameters measuring instruments included in the system 7 of autonomous sensors (see FIG. 1), which primarily include accelerometers and gyroscopes, provide information on accelerations j _x and j _1,2 and pitch angles

and yaw ψ. Based on the measurement of j _x and j _1,2 , estimates are formed in the calculators of the autonomous system

and

used in calculating the mismatch parameters. Gyroscopic sensors allow you to decouple the antenna 3 of the CWG from the angular oscillations of the rocket, which increases the accuracy and stability of target tracking in the direction. Processing the initial information about the range and angular position of the target in the calculator 13 allows you to get additional information about the speed and miss of the rocket relative to the geometric center of the target, as well as its geometric dimensions. Consider the rapprochement scheme of the rocket with the goal (figure 2).

According to figure 2, the coordinates of the target relative to the Z axis are indicated by discrete values Z ₁ , Z ₂ , Z ₃ , the current range values corresponding to the moment of passage of the target three fixed points - r ₁ , r ₂ , r ₃ and the current values of the angular position of the target - φ ₁ , φ ₂ , φ ₃ .

The geometric dimensions of the target are determined by measuring the distance to the target and the angular position of the starting and ending points on the target’s body.

The speed of approach of a rocket with a target is determined on the basis of fixing the time interval when the target passes two predetermined distances.

Missile missile relative to the target is determined on the basis of fixing the current values of the range and angular position when the target passes three given distances.

A three-dimensional graph explaining the algorithm for determining miss missed relative to the target is shown in figure 3

According to figure 3, the location of the rocket (M) and target (T) at some point in time t will be:

where V _m , V _t - rocket speed and targets, respectively.

Then the distance r to the target can be calculated by the formula:

или

or

Where

где

Then

Where

In the special case, α, β, γ are constant. For three different points in time:

and

Defining r ₄ as the limit at which z = z ₄ = 0, we obtain:

Then, after making the transformations, we get:

Missile missiles relative to the target can be represented as an expression:

Where

- постоянные коэффициенты.

are constant coefficients.

Information about the current values of the range and the angular position of the target is supplied to the first and second inputs of the block 14 for fixing the current values of the parameters of motion of the target (figure 4). These signals through the functional converter 18, the first multiplier 19 are supplied to the first inputs of the first 20, second 21 and third 22 comparison circuits, the second inputs of which receive signals from the first constant signal generator 26. When the level of the specified signals from the outputs of the comparison circuits is exceeded, the signals are sent to the first inputs of the first, second and third storage devices, the second inputs of which receive signals proportional to the current range to the target. Thus, from the output of the first 23, second 24, and third 25 storage devices, signals proportionally to the current values of ranges relative to fixed points of space relative to the target are received sequentially in time (Fig. 2). In addition, from the output of the second 21 and third 22 comparison circuits, a signal is received that fixes the moment of passage of two fixed distances Z ₂ and Z _{3 by the} target, and from the fourth output of the constant signal setter 26 is proportional to the initial velocity of the fragments V ₀ .

, который поступает на первый вход блока формирования команды на срабатывание боевой части ракеты (см. фиг.4).Block 15 missile missile determination based on incoming signals proportional to the value of r ₁ , r ₂ , r ₃ generates missile missiles relative to the target (see Fig.6). These signals through the first 27, second 28 and third 29 quadrants are fed to the first inputs of the second 30, third 31 and fourth multipliers, the outputs of which generate signals proportional to the value of A ² r ₁ ² , B ² r ₂ ² , C ² r ₃ , respectively ² These signals are input to the second functional converter 35 through the first 33 subtractor and the second 34 adder. At the output of the functional Converter 35, a signal is generated proportional to the miss miss, in the form of the expression:

, which is fed to the first input of the team formation unit for the operation of the warhead of the rocket (see figure 4).

Block 16 determine the geometric dimensions of the target generates a signal proportional to the geometric dimensions of the target. The input signals that ensure the functioning of the block 16 determine the geometric dimensions of the target are signals about the current range, the angular position of the target, from the output of the receiver 4 reflected signals, as well as signals that determine the moment of passage of the target two fixed distances Z ₂ Z ₃ .

At the moment the target passes the second fixed distance, the signal from the fifth output of the block 14 for fixing the current motion parameters of the target Z _{2 is} fed to the second input of the And 37 element, the first input of which receives the signal from the output of the receiver 4 of the reflected signals, in the presence of these signals from the output of the element, the signal 39 pulse generator. From the output of the pulse generator through the shift register 41 and the DAC 42, the antenna control signal is supplied to the first input of the power amplifier 8 and the antenna drive. When this happens, the space is scanned in a given range (due to the operation of the key 12, the power amplifier 8 and the antenna drive are disconnected from the antenna control channel 11).

The moment of occurrence of the reflected signal from the target captures the initial position of the range and the angular position of the target due to the triggering of the third 43 and fifth 45 storage devices based on the appearance of the signal from the second output of the And 37 element. The moment the signal disappears from the output of the receiver 4 of the reflected signals fixes the final position of the range and the angle the position of the target due to the operation of the fourth 44 and sixth 46 memory devices when a signal is received from the output of the AND-NOT 38 element.

Then these signals are received through the third 47 and fourth quadrator, the third 49 adder, the second 50 subtractor, and also through the third 51 subtractor, the third 52 functional converter, the fifth 54 multiplier by the fourth 53 functional converter, which generates a signal in accordance with the expression

Block 17 forming a team to undermine the warhead of the rocket generates a signal to undermine the warhead of the rocket in accordance with the specific conditions of the approach of the rocket to the target and its geometric dimensions. The input information necessary for the functioning of this unit is information about the moment of passage of the target of the third fixed distance, about the speed of approach, miss the missile relative to the target, the initial speed of the fragments, the geometric dimensions of the target.

This information through the first 56, second 57 and third 58 dividers is fed to the input of the fourth 59 subtracting device, the output of which is in the form of the expression:

From the output of the team formation unit to undermine the signal in accordance with the conditions of the approach and the geometrical dimensions of the target is supplied to undermine the warhead of the rocket.

Thus, in addition to guiding the rocket, a team is formed to undermine the warhead of the rocket.

Sources of information

1. Merkulov V.I., Lepin V.N. Aircraft radio control systems. M .: Radio and communications, 1997, - c.201 (prototype).

Claims (11)

1. The method of functioning of the information and computing system of the rocket, which consists in measuring the parameters of the target’s motion and the rocket’s own motion, forming the necessary parameters of relative and absolute motion that are not directly measurable, based on using a priori information, choosing the method of aiming the rocket at the target, the best for which Either the criterion for the given conditions of use, the analysis of the interference environment and the inclusion, depending on the situation, of the means of noise protection and non-radio engineering measuring instruments, re-targeting the rocket to the jammer, generating a training and control signal for the radio fuse, characterized in that they determine, based on the initial information about the angular position and the distance to the target in the immediate vicinity of the target, the speed of approach of the rocket, the geometric dimensions of the target, miss the missile and form a team to undermine the warhead of the rocket based on this information, taking into account the initial speed of the flight of fragments of the warhead of the rocket. 2. The method according to p. 1, characterized in that they determine the speed of approach of the rocket in the immediate vicinity of the target at the moment the target passes the second and third fixed distances in the form of an expression

where Z ₂ , Z ₃ are the second and third fixed distances to the target, τ is the time interval proportional to the speed of the target when passing through these fixed distances. 3. The method according to p. 1, characterized in that they determine the linear size of the extended target at the moment it passes the second fixed distance by scanning it with a radiation pattern and fixing the angular positions and the distance to the starting and ending points on the extended target, respectively, at the time the reflection appears and disappears signal from the target as an expression

where D ₁ , D ₂ - the angular position of the start and end points respectively on the target body; Δφ = φ _n -φ _to - the angular size of the target. 4. The method according to p. 1, characterized in that they determine the amount of miss in the form

where A, B, C are constant coefficients; r ₁ , r ₂ , r ₃ - current distances recorded during the passage of the target three specified distances. 5. The method according to p. 1, characterized in that they form a team to undermine the warhead of the rocket in the form of an expression

where V ₀ is the initial velocity of the expansion of fragments. 6. A device for the operation of an information-computing system, comprising a serially connected antenna and a receiver of a synchronization signal, an antenna and a receiver of a reflected signal, an information processing module and a mismatch parameters calculator, as well as a system of autonomous sensors, a power amplifier and an antenna drive, an information processing module consists of devices for searching, detecting, selecting and analyzing signals, a channel for estimating the range and speed of approach, an antenna control channel, and its output is fur is connected with the antenna of the reflected signal, the output of the reflected signal receiver is connected to the first input of the information processing module, the second, third, fourth, fifth, sixth, seventh inputs of which are respectively connected to the first output of the synchronization signal receiver, the first and second output of the autonomous sensor system, with the output of the training and target designation instructions from the fighter equipment, which are simultaneously connected to the third input of the mismatch parameters calculator, with the output of the autonomous system calculator, the first the output of the power amplifier and the antenna drive, the second output of which is mechanically connected to the antenna of the reflected signal, while the first, second and third outputs of the information processing module are connected respectively to the input of the control and feedback signals of the fighter equipment, the first and second input of the mismatch parameter calculator, in addition , the second output of the synchronization receiver is connected to the second input of the reflected signal receiver, characterized in that it has a key and a team formation calculator for undermining the combat clock a rocket, the first, second inputs of which are connected respectively to the first and second outputs of the information processing module, the third input is with the output of the reflected signal receiver, the first output is connected to the second key input, the first input of which is connected to the second output of the antenna control channel, and the key output connected to the first input of the power amplifier and the antenna drive, the second input of which is connected to the second input of the team formation calculator for undermining the warhead of the rocket, the third input of which is the team’s output in the warhead of the rocket. 7. The device according to p. 6, characterized in that the calculator of the formation of the command to detonate the warhead of the rocket consists of a unit for fixing the current parameters of the target’s movement, a unit for determining miss missiles, a unit for determining the geometric dimensions of the target, and a unit for forming a team for detonating the warhead of the missile the first and second inputs of the unit for fixing the current parameters of the target’s movement and the unit for determining the target’s geometric dimensions are connected respectively to the output of the channel for estimating the range and speed of approach of the target and the channel antenna board, the first, second, third, fourth, fifth and sixth outputs of the unit for fixing the current target motion parameters are connected respectively to the first, second and third input of the missile miss detection unit, to the second, third input of the command formation unit to detonate the missile warhead and the third and the fourth input of the unit for determining the geometric dimensions of the target, the fifth input of which is connected to the output of the receiver of the reflected signal, and the first output is the second output of the computer forming the command to undermine the combat hour and rockets and connected to the first input of the power amplifier and the drive of the antenna, the second and third output of the unit for determining the geometric dimensions of the target are connected respectively to the fourth and fifth input of the unit for forming a team to detonate the warhead of the rocket, the first input of which is connected to the output of the missile miss detection unit, and the output is the third output of the team formation calculator to undermine the warhead of the rocket. 8. The device according to p. 7, characterized in that the unit for fixing the current parameters of the target’s movement consists of a functional converter, a first multiplier of the first, second and third comparison circuits, first, second and third storage devices, as well as a constant signal generator, and the input is functional the converter is connected to the output of the antenna control channel, and the output is connected to the first input of the first multiplier, the second input of which is connected to the output of the channel for estimating the range and approach speed, and the output to the first inputs of howling, second, third comparison circuits, the second inputs of which are connected respectively to the first, second and third outputs of the constant signal generator, and the fourth output of which is connected to the second input of the command formation unit to undermine the warhead of the rocket, the outputs of the comparison circuits are connected respectively to the first inputs of the first , the second and third storage devices, the second inputs of which are connected to the output of the channel for estimating the range and approach speed. 9. The device according to p. 7, characterized in that the missile miss detection unit consists of the first, second and third quadrators and multipliers, the first subtracting and second summing devices, the second functional converter, as well as the second constant signal generator, the first, second , the third outputs of the block fixing the current parameters of the target’s movement are connected to the inputs of the first, second, and third quadrators, the outputs of which are connected respectively to the first inputs of the second, third, and fourth multipliers; the inputs of which are connected respectively to the first, second and third outputs of the second constant signal generator, the outputs of the second and third multipliers are connected to the first and second inputs of the first subtractor, the output of which is connected to the first input of the second summing device, the second input of which is connected to the output of the fourth multiplier, and the output of the second summing device is connected to the input of the second square root functional extraction converter, the output of which is connected to the first input of the form block command team to undermine the warhead of the rocket. 10. The device according to p. 7, characterized in that the unit for determining the geometric dimensions of the target consists of an element And, an AND element, a pulse generator, a pulse counter and a series-connected shift register, a digital-to-analog converter, and also from the third, fourth, fifth and the sixth storage devices, the third and fourth quadrators, the third adder, the second and third subtracting devices, the third and fourth functional converters, the fifth multiplier of the third constant signal generator, etc. whereby the output of the reflected signal receiver is connected to the first input of the AND element and at the same time the input of the NAND element, the output of the block for fixing the current parameters of the target’s movement is connected to the second input of the And element, the output of which is connected simultaneously with the input of the pulse generator, the first inputs of the third and fifth storage devices, the second inputs of which are connected respectively to the output of the range estimation channel and the antenna control channel, the output of the NAND element is connected to the first inputs of the shift register, the fourth and sixth parts of the omitting devices, the output of the channel for estimating the range and approach speed is connected to the inputs of the third and fourth memory devices, the outputs of which are connected respectively to the inputs of the third and fourth quadrators, the outputs of which are connected to the first and second inputs of the third adder, the output of which is connected to the first input of the second subtractor , the output of the fifth and sixth storage devices is connected respectively to the first and second inputs of the third subtractor, the output of which is connected to the input fun a national converter, the output of which is connected to the first input of the fifth multiplier, the second and third inputs of which are connected respectively to the outputs of the third and fourth storage devices, and the output is connected to the second input of the second subtractor, the output of which is connected to the input of the fourth functional converter, the output of which is connected to the third input of the command formation unit to undermine the warhead of the rocket, the output of the pulse generator is connected to the first input of the pulse counter, and the second input is connected to the poles m is the output of the unit for fixing the current parameters of the target’s movement, and the output of the counter is the second output of the unit for determining the geometric dimensions of the target, the first and third output of which is the output of the digital-analog converter and the fourth functional converter, respectively. 11. The device according to p. 7, characterized in that the unit for forming a command to undermine the warhead of the rocket consists of the first, second and third dividers, the fourth subtracting device, the fourth output of the unit fixing the current parameters of the target’s movement, the output of the miss block and the third output the unit for determining the geometric dimensions of the target are connected to the first inputs of the first, second and third dividers, the output of the channel for estimating the range and approach speed is connected simultaneously with the second inputs of the first and third dividers her, the fifth output of the unit for fixing the current parameters of the target’s movement is connected to the second input of the second divider, the outputs of the first, second and third dividers are connected respectively to the first, second and third inputs of the fourth subtractor, the output of which is the output of the command formation unit to undermine the warhead of the rocket.

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